CN108974333B - Full-oil buffer and compensation device - Google Patents
Full-oil buffer and compensation device Download PDFInfo
- Publication number
- CN108974333B CN108974333B CN201810939959.XA CN201810939959A CN108974333B CN 108974333 B CN108974333 B CN 108974333B CN 201810939959 A CN201810939959 A CN 201810939959A CN 108974333 B CN108974333 B CN 108974333B
- Authority
- CN
- China
- Prior art keywords
- buffer
- cavity
- oil
- compensation
- valve body
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/58—Arrangements or adaptations of shock-absorbers or springs
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Fluid-Damping Devices (AREA)
Abstract
The invention discloses a full-oil buffer and a compensation device, which comprises an upper end cover (1) matched with a sphere surface of an undercarriage body, wherein the upper end cover is hermetically connected with an outer buffer barrel (2), a buffer cavity (A) and a compensation cavity (B) are arranged in the outer buffer barrel, the buffer cavity is arranged right below the upper end cover, the compensation cavity is hermetically connected with an outer compensator barrel (14), and oil passages (2-4) are arranged between the buffer cavity and the compensation cavity and communicated with each other; a piston rod (3) with the upper end fixedly connected with the undercarriage body penetrates through the upper end cover and the outer buffer barrel and is arranged in the buffer cavity, the middle part of the piston rod is provided with an annular end surface to divide the buffer cavity into an upper cavity and a lower cavity, and the annular end surface is provided with a damping hole (3-2) communicating the upper cavity and the lower cavity; the upper end of the compensation cavity is provided with a valve body (6) for controlling an oil passage, the compensation cavity below the valve body is internally provided with a floating piston (12), the upper end surface of the floating piston is provided with an oil storage cavity (12-4), and a piston rod of the floating piston is sleeved with a return spring (13).
Description
Technical Field
The invention relates to an aircraft landing gear, in particular to a full-oil buffer and a compensation device for an unmanned aerial vehicle landing gear.
Background
With the rapid development of the aviation industry, various structural forms of aircraft landing gear bumpers have appeared: steel spiral spring and ring spring buffer, steel sheet spring buffer, rubber spring buffer, full oil buffer, oil gas buffer, etc. Most aircraft now appear to use primarily oil and gas bumpers with higher efficiency and best capacity for absorbing work.
In recent years, small airplanes and unmanned planes are rapidly developed, and landing gears are increasingly developed towards simplification and light weight, such as leaf spring type landing gears. The undercarriage is generally seen by research and development personnel due to the advantages of simple structure, high reliability, easy maintenance and the like.
Although some small aircraft main landing gears can be replaced by leaf springs, the damping performance of the leaf spring type landing gears cannot absorb the large impact capacity due to the fact that the tonnage of some small aircraft is slightly larger, and additional damping devices such as full-oil dampers need to be matched. The traditional full-oil buffer is mostly used for rocker arm type undercarriage, has higher buffering efficiency and reliability compared with the traditional oil-gas buffer, has reliable structure and long service life, and has the defects that the change of oil tissue influences the performance of the buffer and the mechanical friction force is large at low temperature and the like.
Disclosure of Invention
The invention aims to provide a full-oil buffer and a compensation device which have simple structure, reliable use and simple and easy maintenance.
In order to achieve the above purpose, the invention provides a full oil buffer and compensation device, comprising an upper end cover matched with a sphere surface of an undercarriage body, wherein:
the upper end cover is connected with the outer barrel of the buffer in a sealing manner, a buffer cavity and a compensation cavity are arranged in the outer barrel of the buffer, the buffer cavity is arranged right below the upper end cover, the compensation cavity is connected with the outer barrel of the buffer in a sealing manner, and an oil liquid channel is arranged between the buffer cavity and the compensation cavity and communicated with each other;
a piston rod with the upper end fixedly connected with the undercarriage body penetrates through the upper end cover and the buffer outer cylinder to be arranged in the buffer cavity, the middle part of the piston rod is provided with an annular end surface to divide the buffer cavity into an upper cavity and a lower cavity, and the annular end surface is provided with a damping hole for communicating the upper cavity and the lower cavity;
the upper end of the compensation cavity is provided with a valve body for controlling an oil passage, a floating piston is arranged in the compensation cavity below the valve body, the upper end face of the floating piston is provided with an oil storage cavity, and a piston rod of the floating piston is sleeved with a return spring.
The further improvement of the scheme is that the axial direction of the valve body is provided with a stepped hole which is communicated with the oil passage and has a large upper part and a small lower part, a ball body is arranged in the stepped hole, when the aircraft lands, the ball body and a small hole at the lower end of the stepped hole form a spherical surface seal, and when the external environment rises or returns to normal, the ball body is in a free state in the valve body so as to communicate the buffer cavity with the compensation cavity.
The further improvement of the above scheme is that the radial setting of valve body lower extreme crosses the through-hole of shoulder hole, and the through-hole sets up in the top of spheroid position, puts into the stylar that supplies restriction spheroid home range in the through-hole to lose reset action after reset spring surpasss its minimum compression capacity.
The further improvement of the scheme is that a baffle is arranged between the valve body and the floating piston, and the bottom of the valve body is communicated with an oil storage cavity on the upper end face of the floating piston through the baffle.
In a further improvement of the above scheme, the bottom parts of the outer barrel of the buffer and the outer barrel of the compensator are respectively provided with a dustproof ring.
In a further improvement of the above scheme, the upper end surface of the upper end cover is provided with a concave spherical surface matched with the convex spherical surface on the plate spring support column so as to realize the swinging of the piston rod in the vertical direction (relative to the ground).
The further improvement of the scheme is that a sealing ring is arranged between the outer diameter of the annular end face of the piston rod and the inner wall of the buffer cavity to form sealing, so that leakage of oil between the outer diameter of the annular end face of the piston rod and the inner wall of the buffer cavity is avoided.
The technical scheme is further improved in that the middle of a piston rod of the floating piston is provided with an annular step for limiting the maximum compression amount of the return spring.
According to the scheme, the further improvement is that the tail end of the piston rod of the floating piston is provided with a scale mark for monitoring oil.
The invention mainly utilizes the energy consumed by oil flowing through the damping hole on the piston rod, and designs the compensation volume for the change of the oil volume caused by the change of the environmental temperature. When an airplane lands, the oil buffer absorbs energy by the damping hole, the oil pressure of the upper cavity of the buffer cavity is higher, so that the ball blocks the small hole at the lower end of the stepped hole of the valve body, and oil cannot flow into the compensator; when the external environment rises, the volume of the oil expands, the pressure of the buffer cavity is equivalent to that of the compensation cavity, the ball body is in a free state in the valve body, the volume of the expanded oil flows into the compensation cavity, the return spring is compressed along with the increase of the volume of the oil flowing into the compensation cavity, the volume of the corresponding compensation cavity is increased, and when the environmental temperature returns to normal, the return spring returns the oil in the compensation cavity to the buffer.
The full-oil buffer and the compensation device are used for matching with an auxiliary buffer device of a main plate spring type undercarriage of a certain type of unmanned aerial vehicle and a similar impact buffer requirement device, the compensation device bringing oil change according to external environment temperature change is designed besides the buffer efficiency, the oil buffer is combined with the plate spring type undercarriage to carry out a drop test, and the buffer efficiency meets the most serious working condition of aircraft landing.
The invention has simple structure, easy operation and maintenance, obvious buffer effect of the auxiliary plate spring type undercarriage and good performance.
Drawings
Fig. 1 is a schematic view of the installation of the invention on a leaf spring landing gear.
FIG. 2 is a schematic view of an assembly of the full oil buffer and the compensating device.
Fig. 3 is a partial enlarged view of fig. 2 at point i.
Fig. 4 is a schematic view of an upper end cap of the full oil buffer.
FIG. 5 is a schematic view of the damper outer barrel.
Fig. 6 is a schematic view of a piston rod.
FIG. 7 is a schematic view of a compensator valve body.
Fig. 8 is a schematic view of a compensator floating piston rod.
Fig. 9 is a schematic view of a compensator spring.
Fig. 10 is a schematic view of the compensator outer cylinder.
FIG. 11 is a schematic diagram of the operation of a full oil buffer and compensator (black texture in the figure represents oil).
FIG. 12 is a schematic diagram of the oil flow direction for a full oil buffer and compensator with increasing temperature (black texture in the figure represents oil).
Detailed Description
The invention is further illustrated with reference to the following figures and examples.
As shown in fig. 2 and 3, the full oil buffer and compensation device of the invention comprises an upper end cover 1 matched with the spherical surface of the landing gear body, a buffer outer cylinder 2, a piston rod 3 with a damping effect, a valve body 6 for controlling an oil passage, a needle post 8, a ball 9, a floating piston rod 12, a return spring 13, a compensator outer cylinder 14, a baffle plate 10, a sealing ring 4/5/7/11/16/17 and a dust ring 15/18.
As shown in figures 2 and 4, a concave spherical surface 1-1 is arranged on the upper end surface of an upper end cover 1 and is matched with the upper spherical surface of a plate spring support to form a spherical surface pair, an annular sealing groove 1-2 is arranged on the inner diameter of the upper end cover and is provided with a sealing ring 4, the sealing ring and a piston rod 3 form a cylindrical pair, threads 1-3 are arranged on the outer diameter surface of the upper end cover and are matched with a buffer outer cylinder 2 in a threaded mode, and a sealing ring 5 is arranged at the.
As shown in figures 2 and 5, the buffer outer cylinder 2 is provided with two cavities, one is a buffer cavity A, the other is a compensation cavity B, and a channel 2-4 is arranged between the two cavities. The upper end of the buffer cavity A is provided with an internal thread 2-1, the surface of the inner wall of the oil cavity is hardened, and the lower end of the oil cavity is provided with an annular sealing groove 2-2 and a dustproof ring groove 2-3. The compensation cavity B of the buffer outer cylinder 2 is provided with an annular seal groove 2-5, and the lower end is provided with an internal thread 2-6 which is in threaded fit with the compensator outer cylinder 14.
As shown in figures 2 and 6, the upper end of a piston rod 3 is provided with an external thread 3-1 which is connected with a joint bearing lifting lug of an undercarriage body to be matched with the buffer to swing in the vertical direction when the aircraft lands, the middle part of the piston rod is provided with an annular end face which is provided with a damping hole 3-2, the oil is supplied to the buffer during the compression process and the energy is consumed by the oil flow, the outer diameter of the annular end face is provided with an annular sealing groove 3-3 which forms sealing with the inner wall of a buffer cavity A through a sealing ring 16 to prevent the oil from flowing through, and the tail end of.
As shown in fig. 2, 3 and 7, an annular sealing groove 6-1 is formed in the outer diameter surface of the valve body 6 for placing a sealing ring 7 between the valve body 6 and the buffer outer cylinder 2, a stepped hole is formed in the axial direction of the valve body, a through hole 6-2 is radially formed in the lower end of the valve body, and a needle 8 is inserted into the through hole 6-2 after the ball 9 is placed in the stepped hole to limit the moving range of the ball 9.
As shown in fig. 2, 8 and 9, an oil storage cavity 12-4 is formed in the upper end surface of the floating piston 12, an annular sealing groove 12-1 is formed in the large outer diameter surface to allow a sealing ring 11 to be placed in and form a sealing structure with a compensator outer cylinder 14 to prevent oil from leaking through the compensator, an annular step 12-2 is arranged in the middle to limit the maximum compression amount of a return spring 13, and a process hole 12-3 and a scale line for monitoring whether the oil leaks are arranged at the tail end of the return spring.
As shown in figures 2, 5 and 10, the outer surface of the compensator outer cylinder 14 is provided with external threads 14-1 which are matched with the threads of the buffer outer cylinder 2 and form a sealing structure with a sealing ring 11 in an annular sealing groove 2-5 of the outer cylinder, and the lower end of the compensator outer cylinder is provided with a dustproof ring groove 14-2 for installing a dustproof ring 15.
As shown in fig. 11, which is a working principle diagram of the full-oil buffer, when an airplane lands, the buffer outer cylinder 2 moves downwards, the piston rod 3 is connected with the undercarriage body and is fixed except for the swinging vertical position, and the buffer cavity a is divided into an upper cavity and a lower cavity by the buffer outer cylinder 2 and the piston rod 3. When the buffer outer cylinder 2 moves downwards, the volume of the upper cavity is reduced, the volume of the lower cavity is increased, the volume of oil in the upper cavity is compressed, and the oil consumes impact energy through the damping holes 3-2 on the annular end face of the piston rod 3. Meanwhile, the upper cavity forms larger pressure due to larger impact energy, so that a ball 9 in the compensator is pressed on a small hole at the lower end of an axial stepped hole of the valve body 6 to form spherical seal, an oil passage is blocked, and the oil in the buffer can only consume energy through the damping hole 3-2 to achieve the buffering effect.
Fig. 12 is a schematic diagram illustrating the operation of the full oil buffer and the compensating device in which the volume of oil changes due to the increase of the external temperature. When normal ambient temperature, the oil of full fluid buffer mainly stores in the cushion chamber A that upper end cover 1 and buffer urceolus 2 formed, and fluid volume increase when ambient temperature risees, if the no space of increased volume is stored and will be suppressed pressure in the inner chamber and lead to pressure very big, produce fatal destruction to buffer seal structure. The environmental temperature rises slowly, the oil volume increases slowly, the pressure of the buffer cavity A and the pressure of the oil storage cavity 12-4 are almost balanced at the moment, the ball 9 is in a free state in the valve body 6, the oil volume increase of the buffer cavity A flows into the compensation cavity B and the oil storage cavity 12-4 along the arrow direction in the figure, the floating piston rod 12 compresses the return spring 13 to enlarge the compensation cavity B along with the increase of the oil volume, and sealing structures are arranged between the compensator outer cylinder 14 and the buffer outer cylinder 2 and between the compensator outer cylinder 14 and the floating piston 12 to prevent the oil from leaking. When the external environment temperature returns to normal, the oil in the compensation chamber B returns to the buffer chamber a under the action of the return spring 13.
Claims (9)
1. A full oil buffer with a compensation device comprises an upper end cover (1) matched with a sphere surface of an undercarriage body, and is characterized in that,
the upper end cover is connected with the buffer outer barrel (2) in a sealing manner, a buffer cavity (A) and a compensation cavity (B) are arranged in the buffer outer barrel, the buffer cavity is arranged right below the upper end cover, the compensation cavity is connected with the compensator outer barrel (14) in a sealing manner, and oil liquid channels (2-4) are arranged between the buffer cavity and the compensation cavity and communicated with each other;
a piston rod A (3) with the upper end fixedly connected with the undercarriage body penetrates through the upper end cover and the outer buffer barrel and is arranged in the buffer cavity, the middle part of the piston rod A is provided with an annular end surface to divide the buffer cavity into an upper cavity and a lower cavity, and the annular end surface is provided with a damping hole (3-2) communicating the upper cavity and the lower cavity;
the upper end of the compensation cavity is provided with a valve body (6) for controlling an oil passage, the compensation cavity below the valve body is internally provided with a floating piston (12), the upper end surface of the floating piston is provided with an oil storage cavity (12-4), and a piston rod B of the floating piston is sleeved with a return spring (13).
2. The full oil buffer with the compensation device according to claim 1, wherein the valve body is axially provided with a stepped hole which is communicated with the oil passage and has a large upper part and a small lower part, a ball (9) is placed in the stepped hole, the ball forms a spherical seal with the small hole at the lower end of the stepped hole when the aircraft lands, and the ball is in a free state in the valve body when the external environment rises or returns to normal so as to communicate the buffer chamber with the compensation chamber.
3. The full oil buffer with the compensation device according to claim 2, wherein the lower end of the valve body is radially provided with a through hole (6-2) crossing the stepped hole, and the through hole is arranged above the position of the ball body, and a needle (8) for limiting the moving range of the ball body is arranged in the through hole.
4. The full oil buffer with the compensation device according to claim 1, wherein a baffle (10) is arranged between the valve body and the floating piston, and the bottom of the valve body is penetrated through the baffle and communicated with an oil storage cavity on the upper end surface of the floating piston.
5. The full oil buffer with the compensation device as claimed in claim 1, wherein the outer buffer cylinder and the outer compensator cylinder are provided with dust rings at the bottom respectively.
6. The full oil buffer with compensation device as claimed in claim 1, wherein the upper end surface of the upper end cap is provided with a concave spherical surface (1-1) matching with the convex spherical surface of the leaf spring strut.
7. The full-oil buffer with the compensation device as claimed in claim 1, wherein a sealing ring is arranged between the outer diameter of the annular end face of the piston rod A and the inner wall of the buffer cavity to form a seal.
8. The full oil buffer with a compensator according to claim 1, wherein the floating piston has an annular step (12-2) in the middle of the piston rod B for limiting the maximum compression of the return spring.
9. The full oil buffer with the compensation device as claimed in claim 1, wherein the end of the piston rod B of the floating piston is provided with a scale mark for monitoring oil.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810939959.XA CN108974333B (en) | 2018-08-17 | 2018-08-17 | Full-oil buffer and compensation device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810939959.XA CN108974333B (en) | 2018-08-17 | 2018-08-17 | Full-oil buffer and compensation device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108974333A CN108974333A (en) | 2018-12-11 |
| CN108974333B true CN108974333B (en) | 2020-04-10 |
Family
ID=64553997
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810939959.XA Active CN108974333B (en) | 2018-08-17 | 2018-08-17 | Full-oil buffer and compensation device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108974333B (en) |
Families Citing this family (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111559214B (en) * | 2019-02-14 | 2021-09-28 | 徐州徐工液压件有限公司 | Oil gas suspension and mining dump truck |
| CN110159699A (en) * | 2019-05-17 | 2019-08-23 | 四川凌峰航空液压机械有限公司 | The recharging oil device of pressure compensation hydraulic damper |
| CN110254721B (en) * | 2019-07-10 | 2023-07-18 | 河海大学常州校区 | Buffer platform is put in air |
| CN110282134B (en) * | 2019-07-10 | 2023-07-14 | 河海大学常州校区 | Buffer platform is put in air |
| CN111196352B (en) * | 2020-01-17 | 2021-07-23 | 中国商用飞机有限责任公司 | Buffer and tail skid including the same |
| CN111470036B (en) * | 2020-04-30 | 2023-05-23 | 中国飞机强度研究所 | Anti-falling single-leg buffer structure and leg landing gear |
| CN115325098B (en) * | 2022-09-05 | 2024-03-26 | 江苏电子信息职业学院 | Damping device for textile machinery |
Family Cites Families (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB525266A (en) * | 1939-01-19 | 1940-08-26 | Dunlop Rubber Co | Improvements in or relating to fluid-pressure apparatus for controlling the operation of brakes for aircraft |
| CN2412780Y (en) * | 1999-12-13 | 2001-01-03 | 吴林须 | Plunger hydraulic lift pump for tractor front cover assembly |
| CN2692005Y (en) * | 2004-04-21 | 2005-04-13 | 重庆长安减震器有限公司 | Adjustable compression damping aeration type rear shock absorber |
| FR2922190B1 (en) * | 2007-10-11 | 2010-04-09 | Eurocopter France | RETRACTION CYLINDER, GYRO AERIAL LIGHTER PROVIDED WITH SUCH A RETRACTION CYLINDER |
| CA2711199C (en) * | 2010-07-29 | 2013-11-12 | Messier-Dowty Inc. | Hydraulic shimmy damper for aircraft landing gear |
| CN102748422B (en) * | 2012-07-04 | 2013-11-20 | 吉林大学 | Stroke sensitive damping adjustable shock absorber |
| CN203362668U (en) * | 2013-01-31 | 2013-12-25 | 杨洁 | Balance valve of dynamic load differential pressure protection and flow pressure air chamber compensation |
| CN205779980U (en) * | 2016-06-27 | 2016-12-07 | 江苏建筑职业技术学院 | Can precision control temperature-compensating valve |
| CN106838096B (en) * | 2017-03-24 | 2018-05-22 | 中国北方车辆研究所 | Hydro-pneumatic spring self-lubricating compensates floating piston |
| CN107461374B (en) * | 2017-09-08 | 2020-03-27 | 中航飞机起落架有限责任公司 | Hydraulic control valve of undercarriage retractable actuator cylinder |
-
2018
- 2018-08-17 CN CN201810939959.XA patent/CN108974333B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN108974333A (en) | 2018-12-11 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108974333B (en) | Full-oil buffer and compensation device | |
| CN107339360A (en) | A kind of undercarriage buffer | |
| CN100430622C (en) | Undercarriage bumper having inner flow regulating valve | |
| US3696894A (en) | Acceleration sensitive shock absorber valve | |
| CN203247729U (en) | Viscous damper with static rigidity | |
| CN206972817U (en) | A kind of spring air damper | |
| CN110345187B (en) | Composite self-resetting energy dissipation and shock absorption device and using method thereof | |
| CN111442058A (en) | Hybrid shock-absorbing device | |
| CN203836056U (en) | Buffer for helicopter | |
| US3078967A (en) | Shock strut with linear damper | |
| CN206054606U (en) | A kind of non-linear hydraulic damper | |
| CN105626738A (en) | Aircraft undercarriage mixed damping method | |
| CN105020316A (en) | Undercarriage buffer | |
| CN1978936A (en) | Flow-throttling hole hydraulic buffer | |
| CN108589800B (en) | Basic earthquake-resistant structure of building engineering | |
| CN104154168B (en) | A kind of miniature noise elimination accumulator for damper | |
| CN109115255B (en) | Clamping groove cut-off type anti-disturbance impact isolation platform | |
| CN207403927U (en) | A kind of shock absorption buffering mechanism of large size fixed-wing unmanned plane | |
| CN106704444A (en) | Aircraft taking off and landing suspension method | |
| CN110159696A (en) | Composite buffering damper | |
| CN105626740A (en) | Multistage damping shock-absorbing apparatus | |
| CN111692263A (en) | Buffer folding and unfolding integrated anti-crash buffer for oil-gas type undercarriage | |
| CN205592221U (en) | Hatch door pressurized strut | |
| CN111140619A (en) | Damping valve of hydraulic shock absorber and hydraulic shock absorber | |
| CN206175548U (en) | Double -acting cylinder body bumper shock absorber |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |